Complex system of preparation, navigation, and control of aerial vehicle
SUBSTANCE: invention refers the area of aviation instrument engineering and may be used in complexes of flight control and navigation equipment of an aerial vehicle (AV). For such purpose, the complex system of preparation, navigation, and control of an aerial vehicle including the ground system of flight assignment preparation (SFAP) for AV and the onboard navigation complex (NC) of AV, the connection between which is performed by means of a portable data storage (PDS) of a universal flash-drive type, moreover, SFAP consists of the a universal data recording device to PDS and universal interface devices connected via inputs/outputs to an electronic unit, and NC consists of a data reading device from PDS, a set of multifunctional indicators, a set of flight control and navigation systems, an onboard radio-technical communication system, and an onboard digital computing system (ODCS), which distinguishes by the fact that a computing logical functional module (CLFM) of formation of an arbitrary trajectory (AT) graphical projection and CLFM of decomposition of an AT graphical projection to several straight-line microtrajectories (SMT) are additionally introduced into the electronic unit, and the second CLFM of decomposition of an AT graphical projection is additionally included into ODCS. All these systems are interconnected via the traffic channel (TC). Whereupon, interconnection points of SMT during a flight along AT are used in the system as navigation point equivalent by their properties to "standard" navigation points of the main flight route. The introduction of additional units provides the extension of functional capabilities of the system and, consequently, of AV by means of the increasing of process automation rate of AV control during a flight along an arbitrary trajectory.
EFFECT: invention allows extending of functional capabilities of an aerial vehicle.
SUBSTANCE: invention relates to determination of parachute system altitude above earth surface. Proposed method consists in determination of aircraft altitude and descent altitude to parachute deployment. Additionally, prior to jumping, mean descent speed of parachute system if deployed main parachute and parachute system descent time are determined. Parachute system descent time after parachute deployment is defined by descent time and mean descent speed to subtract obtained magnitude fro parachute system altitude at parachute deployment. Altitude above the earth is identified above the earth.
EFFECT: higher accuracy, fast response.
FIELD: physics, computer engineering.
SUBSTANCE: group of inventions relates to self-contained digital integrated systems of on-board equipment of multi-engine aircraft. The on-board information support system comprises a take-off dynamics module, an altitude-speed and meteorological parameter module, a flight characteristics module, an aerodynamics module, an engine thrust module, an aerodrome database module and a global database of the topography of the underlying surface EGPWS of high precision in 3D format and minimum safe altitude, an analysis and decision-making module and other modules. The disclosed cognitive format of presenting information on a flight display includes a synthesized display of the runway with an axial line, the runway threshold, display of the boundaries of maximum allowed lateral deviation of aircraft take-off run and other vital displays. The flight display, on the background of the windscreen, further displays commands to raise the nose wheel, take-off, accelerate the aircraft to safe climbing speeds and commands to maintain an optimum pitch angle at the airborne part of the take-off distance, as well as commands to turn and emergency climb to prevent collision with the underlying surface and manmade obstacles. The formats of said parameters are displayed using principles of activating visual perception of information in information support of the crew in cognitive operations of the crew using principles of artificial intelligence, completeness of information presentation, relevancy and interactivity.
EFFECT: easier control of aircraft and safer flights.
20 cl, 10 dwg, 3 tbl
FIELD: instrument making.
SUBSTANCE: this complex comprises inertial orientation system (IOS) built around coarse sensors. Said ISO is connected to computation platform and incorporates three accelerometers connected in ISO three perpendicular axes and three transducers of angular velocities. Besides, it includes three-axis magnetic compass and hydrostatic assy of inclination (HAI). The latter comprises three differential hydrostatic pressure transducers connected in three perpendicular HAI axes, at the ends of equal-length bases. This invention consists in application of signals of said accelerometers and three transducers of angular velocities for computation of orientation angles by means of calculation of the matrix of guide cosines between bound and navigation systems of coordinates. Acceleration errors of said accelerometers are compensated for, accelerations from said bound system are converted into navigation system and current velocities and coordinates increments are defined. Said three differential hydrostatic pressure transducers connected in three perpendicular HAI axes and three-axis magnetic compass are used to make the measurements. Reading of said compass and said transducers are used to calculate angles of inclination between bound and navigation systems of coordinates and to compute the azimuth from compass readings. Obtained magnitudes are applied to correct the readings of accelerometers and angular velocity transducers.
EFFECT: higher accuracy of navigation parameters determination.
FIELD: radio engineering, communication.
SUBSTANCE: method is carried out through automatic use of two modes when operating on a route: satellite navigation equipment (SNE) mode and Memory mode. In the first mode, output coordinates of the SNE are the output coordinates of the integrated coordinate calculation equipment (ICCE). Upon contact with a small number of satellites (less than four), the ICCE automatically switches to operation of the coordinate calculation equipment with initial coordinates which are equal to the last coordinates acquired by the SNE and coordinate increments on path and heading systems calibrated in the first mode.
EFFECT: high accuracy of integrated coordinate calculation equipment during pauses in operation of satellite navigation equipment by introducing periodic calibration of the coordinate calculation equipment on the path.
FIELD: weapons and ammunition.
SUBSTANCE: battle robotic platform comprises a control computer, a control unit, functional subsystems, hardware facilities, the navigation equipment, the sensors, the communication devices, power supply system, the matching devices. The control system in the information-management part has the structure of the type of "star", the central element of the control system is a control computer which provides control and management of all subsystems of the platform and having the Ethernet interface.
EFFECT: provision of the platform motion along the given algorithm in manual and automatic modes, geo location and navigation, control of actuators of chassis, the telecode video information exchange of the platform with the remote control unit.
FIELD: radio engineering, communication.
SUBSTANCE: information on pressure and geometric altitude is received on-board the aircraft to be evaluated in flight and aircraft flying in the vicinity of the satellite navigation receiver to be evaluated from n surrounding aircraft over a channel of standard automatic dependent surveillance (ADS) equipment. On the aircraft to be evaluated, the difference between the pressure and geometric altitude is calculated for each of the n surrounding aircraft and the obtained values are averaged; the difference between the pressure and geometric altitude for the aircraft to be evaluated is determined and the averaged altitude difference is compared with the altitude difference of said aircraft. Air pressure and temperature adjustments are made in accordance with a static atmosphere differential equation. To obtain ADS data from the monitored aircraft, ground-based ADS control integrity of consumer navigation equipment for all monitored aircraft.
EFFECT: broader functional capabilities.
2 cl, 1 dwg
FIELD: instrument engineering.
SUBSTANCE: system comprises three accelerometers with orthogonal axes of sensitivity, a unit of determination of angular orientation matrix of the object, a unit of calculating the derivatives of the angular orientation matrix, and a unit of generation of velocity increments connected in series with the unit of generation of the object velocities, the unit of generation of incremental displacements and the unit of generation of the object coordinates, rigidly mounted on orthogonal axes of sensitivity of the mobile object from the first to the third gyroscopes, the unit of assessment of gravitational acceleration, the non-autonomous radio navigation system connected by radio line to the unit of airborne radio instrument of the object, the unit of assessment of instrumental errors, from the first to the fifth correction units, the adder, the unit of determining apparent accelerations, the first and the second subtracting units.
EFFECT: improving accuracy of autonomous work of the inertial navigation system when interruption of radio contact with external non-autonomous navigation system.
4 cl, 8 dwg, 3 tbl
SUBSTANCE: invention relates to helicopter flight data displays. This indicator comprises the display to indicate reference index "aircraft" fixed relative to the centre to indicate current position of helicopter in space and moving index "Leader" that can turn about its mirror axis and to displace in vertical and horizontal relative to said index "Aircraft: and to display required position in space, symbol generator connected with said display, "Leader" index drive composed by "Leader" characteristics computer. Indices "Aircraft" and "Leader" can display glide and pitch angles by outputting the triangle with its base equal to the length of straight horizontal line indicating aircraft wings while its vertex corresponds to pitch and glide angles of "Aircraft" index and to deflection therefrom of "Leader" index. Besides, this indicator incorporates extra unit for control over helicopter in-flight payload consumption, helicopter speed indicating unit, helicopter current and preset speed indication indices, unit for computation of the centres of weight and moments of inertia.
EFFECT: higher safety, simplified flight control in horizontal route section.
FIELD: instrument engineering.
SUBSTANCE: invention can be used in small-sized strapdown inertial navigation systems (SINS) integrated with a variety of external systems of unmanned aerial vehicles (UAVs). SINS comprises: a unit of sensing elements (SE), a unit of calculation of linear and angular velocities and geographical coordinates, a unit of generating the signals of damping, the units of quaternion calculations, the unit of calculation of the matrix of directing cosines and angles of orientation, the receiver of signals of satellite navigation system (SNS), the unit of determining the quality of SNS signal, the switch of vector signals, the first and second adders-subtractors of vector signals, the unit of air data system (ADS), the unit of determining the heading error, the unit of determining and correction of the wind speed.
EFFECT: improvement of accuracy.
FIELD: instrument engineering.
SUBSTANCE: invention can be used in small-sized strapdown inertial navigation systems (SINS) integrated both with a satellite navigation system (SNS) and with the odometer system for use in mobile onshore devices of different types. The system comprises a unit of sensing elements (SE), a unit of calculating linear and angular velocities and the geographical coordinates, the unit of generation of signals of damping, the first and second units of quaternion calculations, the unit of calculating the matrix of the directing cosines and angles of the system orientation, the receiver of signals of the satellite navigation system (SNS), the unit of determining the quality of SNS signal, the switch of the vector signals, the first and second adders-subtractors of the vector signals, the unit of correction of course angle, and also the wander of directional (azimuth) gyroscope, the unit of stop-detector, the unit of the odometer system with a plurality of connections of different signals between the units and switching connections in different manoeuvres of the object-carrier of SINS.
EFFECT: improvement in accuracy when using coarse or moderate-accurate sensitive elements of SINS.
FIELD: navigation of on-water and underwater vessels.
SUBSTANCE: side surface of underwater object has two static stress detectors which are mounted in opposition to each other and are made in form of fiber coils being optically connected with coherent light source and photoreceiver. Spring-loaded screen is mounted onto nose part of floating vehicle; the screen is mounted for movement along axis of floating vessel. Side surfaces of screen have different lengths. End switch is mounted at shorter side of screen which screen is connected with controlled inputs of propulsive device and steering gear of floating vehicle by means of electric terminals.
EFFECT: widened operational capabilities.
2 cl, 2 dwg
FIELD: control and navigational equipment.
SUBSTANCE: the invention refers to the sphere of control and navigation and may be used on flying vehicles of different types and functions: aircraft, helicopters, airfoil boats and airships and also on water and land transportation vehicles. Integrated flight-navigational complex has an inertial navigational system 1 and a satellite navigational system of automatic dependant observation 2, sensors of air parameters system 3, computing system 4, a system of input data and executive instructions 5, connected to the computing system, a multifunctional system of indication and signaling 6 , a concentrator 7, a computer 8, a bus of data exchange 9, adapters 10,interface modules 11, drives 12 and sensors 13 of a flight control system, drives 14 and sensors of a system of control of a power plant's thrust vectors and sensors 16 of airborne systems. The flight-navigational complex is fulfilled on the basis of unified apparatus and program-computing means providing navigation, flight control and thrust vectors of the power plant and also execution of control and evaluation of the state of the airborne systems and the aggregates of the flying vehicle in the process of exploiting.
EFFECT: increases degree of integration of the complex with airborne systems and safety of a flight of a flying vehicle; due to integration with other airborne systems the complex has lesser mass and dimensions, little expenditure of energy.
FIELD: traffic control.
SUBSTANCE: mode of giving assignment for traffic route is that traffic route assignment is executed in the direction opposite to the moving of a flying vehicle from the aiming point to the point of the beginning of the route.
EFFECT: increases efficiency in exploiting.
2 l,2 dwg
FIELD: procedure of indirect measurements of flight vehicle attitudes.
SUBSTANCE: the method is based on the use of information from the receiver of the satellite navigation system measuring the light vehicle velocity components to the South, East and in altitude from three-coordinate angular velocity and linear acceleration transducers installed on board the flight vehicle. The flight vehicle attitudes are measured in compliance with the estimation algorithm realized in the computer, on the varying time interval.
EFFECT: enhanced accuracy of measurement of the bank, pitch angle and the flight vehicle heading in the conditions of maneuvering.
FIELD: the invention refers to instrument-making industry and may be used at making inertial navigational systems.
SUBSTANCE: the inertial navigational system installed on an object has a mobile platform mechanically connected with an engine installed on the object which has a sensor of forward or angular movement connected through a transmitting unit with a computing unit and an additional mobile platform on which another sensor is installed. The platforms are fulfilled two-stepped and measuring axles of sensors installed on them are perpendicular to inner axles of the platforms. The transmitting unit is fulfilled in the shape of sliding contacts. The sensors of angular and forward movement are connected with an airborne calculator through the transmitting units located along the external and the inner axles of platforms. The inner axis of each platform is mechanically connected with a proper controlled engine installed on the object. The controlled engines installed on external axles of the platforms are connected with the computing units through the transmitting units located along the external axles of the platforms and the controlled engines installed on the object are connected with the computing unit directly.
EFFECT: the invention increases dynamic accuracy of recovery of angular and forward moving objects.
SUBSTANCE: system has block for forming free discrepancy, first and second inputs of which are connected to output of base navigation system and output of correction means block respectively. Block for selection of estimates and discrepancies, by first and second input are connected to output of block for forming a discrepancy and output of block for forming free discrepancy respectively.
EFFECT: higher precision.
FIELD: instrument engineering.
SUBSTANCE: system can be used for controlling flying vehicles. Motion parameter detector is introduced into the system additionally. Input/output of the detector is connected with data exchange line. Computational system has closing error forming unit, speed of wind estimating unit, wind speed predicting unit, speed vector back calculating unit, speed vector re-projecting unit and angle of attack and slip angle calculating unit.
EFFECT: widened operational capabilities.
FIELD: instrument engineering.
SUBSTANCE: system can be used for controlling flying vehicles. Memory unit and long-term adaptation unit are introduced into the system additionally. Input/output of memory unit is connected to first input/output of long-term adaptation unit. Second input/output of long-term adaptation unit is connected to input/output of prediction and evaluation unit.
EFFECT: improved precision.
FIELD: measurement technology.
SUBSTANCE: device can be used in moving objects navigation systems, automatic pilots of model aircraft and mobile complexes of observing systems. Navigation device on the base of micro-mechanical sensitive elements has protective housing with outputs. Inside the housing the integrated platform-free inertial navigation system with micro-mechanical sensitive elements is disposed as well as sensitive element circuit provided with data processing circuit, two circuits connected with sensitive element circuit and/or with each other by adjusting members of electromechanical mounting. One of the circuits is made in form of receiver-transmitter circuit provided with aerial for receiving and transmitting data from on-ground tracker and the second one is made in form of satellite navigation receiving circuit provided with corresponding satellite aerial. Protective housing is provided with radio-transparent cap. Outer side of the housing has cavity for placing accumulator , this side also has adjusting protrusions with magnet supports for fixing onto moving object. Unified integrated platform-free inertial navigation system has micro-mechanical gyroscopes and accelerometers placed inside the housing, as well as sensitive element circuit, circuit for processing data received from sensitive elements, platform-free inertial unit microcontroller integrated circuit, platform-free inertial navigation system microcontroller integrated circuit and at least two micro-mechanical gyroscope circuits and/or accelerometers mounted in perpendicular to sensitive element circuit and fastened tight with it.
EFFECT: widened functional and operational capabilities; prolonged service life.
4 cl, 6 dwg
FIELD: aeronautical engineering; onboard electronic equipment used for navigation and guidance; use of counter-measures.
SUBSTANCE: proposed complex includes set of multi-functional indicators interconnected by inputs and outputs in information exchange channel, windshield indicator, outside-cabin observation TV camera, on-line control elements, set of observation and sighting means, set of navigational and pilotage means, portable initial data carrier, counter-measure control system and computer system. Computer system includes logic elements of combined data base interconnected by inputs and outputs in computer information exchange line, elements of forming navigational and pilotage parameters, sighting and pilotage parameters, forming displayed information, input, output and control of information exchange, synthesizing parameters of motion relative to air medium, synthesizing target designation parameters, control of combat situation and training situations.
EFFECT: extended functional capabilities; enhanced efficiency of multi-mission aircraft.